• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a blade comprising an aerodynamic portion (21) and an assembly of the aerodynamic portion to a blade root retaining the aerodynamic portion in a radial direction (23). The blade root comprises at least one passage restriction in at least one direction of retention orthogonal to the radial direction, having a restricted width allowing the passage of the aerodynamic portion (21). The base of the aerodynamic portion (21) has a total overall space strictly greater than said restricted width, so that in case of rupture of the assembly, the base is able to abut against the restriction of passage so as to retain the aerodynamic portion (21) in the blade root (20).
    公开号:FR3021030A1
    申请号:FR1454283
    申请日:2014-05-14
    公开日:2015-11-20
    发明作者:Bruno Petellaz；Catherine Delmas；Stanislas Tutaj
    申请人:Ratier Figeac SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to a blade, in particular a blade of a rotary machine, in particular a turbine engine.
    [0002] The invention relates more particularly to a propeller blade propulsion and / or lift of an aircraft and / or control yaw. The invention also relates to a propeller, in particular an aircraft turbomachine propeller, comprising at least one blade according to the invention, as well as a turbomachine and an aircraft.
    [0003] In particular the invention provides a propeller blade whose attachment in a propeller hub is improved and in particular secured. A propeller blade is fixed in a propeller hub by the blade root which has anchoring means in the hub along a longitudinal axis of the blade, so along a radial axis of the hub. Often the blade root comprises an anchoring fur providing a mechanical connection and an anchoring in the hub, and a fixing to the aerodynamic portion of the blade. In addition, the turbomachine blades are subjected to very large forces, so that the assembly of the aerodynamic portion at the blade root must be sufficiently strong to both retain the blade in the hub, transmit the movement of the hub to blades and transmit the forces of the blades to the hub (propulsion of the aircraft in particular). The blade root and more particularly the anchoring fur and the fixing of the aerodynamic portion at the blade root are therefore subjected to high stresses - especially during high acceleration - and high vibration levels. They are also subject to significant efforts continuously and prolonged during long flights, and shocks in the event of collisions of a blade with a bird for example. In case of rupture of the assembly of the aerodynamic portion in the blade root, while the propeller is rotating, part of the blade is sometimes released, which can have serious consequences for the aircraft and its components. occupants, or for people and buildings on the ground.
    [0004] FR2984847 describes a blade whose aerodynamic portion is fixed in an anchoring fur of the blade root itself anchored radially relative to the hub. In such a blade the main anchorage of the aerodynamic portion at the blade root is provided by a set of pins and root loops. A redundant secondary anchorage is provided, in case of breakage of the main anchorage, by an additional pin mounted with a clearance in an additional root loop. However, the manufacture and assembly of such a blade are complex and therefore long and expensive because of the high number of root loops and root pins to mount. In addition, the secondary anchoring ensuring safety is not functional in normal operation and therefore strike the weight and cost of the blade. The invention therefore aims to overcome these disadvantages. The invention aims to provide a blade in which the anchoring 15 of the aerodynamic portion in the blade root is ensured, even in case of breakage of the main assembly of the aerodynamic portion in the blade root. The invention also aims to provide such a blade that is simple and fast assembly. The invention aims to provide such a blade that is safe and reliable. The invention also aims to provide such a blade which is easy to manufacture. The invention also aims at providing such a blade whose weight and cost are not substantially modified by the technical solution ensuring anchoring safety in case of failure. Throughout the text, one designates in the traditional way by "extrados" one of the two main faces of a blade adapted to create a suction of the blade by the air flowing along the extrados, the leading edge towards the trailing edge of the blade. Similarly, the term "lower surface" designates the main face 30 opposite the extrados adapted to create a thrust of the blade by the air flowing along the intrados, from the leading edge to the trailing edge of the blade.
    [0005] Throughout the text, the term "rope" designates a direction passing through the leading edge and the trailing edge of the blade. Similarly "longitudinal" means a direction substantially parallel to a straight line connecting the blade root to the free end of the blade. The "span" of the blade represents the maximum distance between the blade root and the free end of the blade. In addition, the term "thickness" refers to the distance at any point between the extrados and the intrados. The invention therefore relates to a blade comprising: - a blade root, - an aerodynamic portion of which part, said base extends into the blade root, - an assembly, said blade foot assembly, of the portion aerodynamic at the blade root retaining the aerodynamic portion in a direction, said radial direction, corresponding to a centrifugal direction when the blade is rotated with the blade root anchored to a rotating hub, characterized in that: - the blade root comprises at least one restriction of passage in at least one direction, said direction of retention, orthogonal to the radial direction, said passage restriction having, in said direction of retention, a dimension, called restricted width, allowing the passage of the aerodynamic portion; through the passage restriction, - the base extends radially inward with respect to said passage restriction, and has a bulk overall in said direction of retention strictly greater than said restricted width, so that in the event of breakage of the blade root assembly, the base is able to abut in said radial direction against the passage restriction so as to retain the aerodynamic portion in the blade root at least in said radial direction. Throughout the text, the term "radial" designates a radial direction relative to a rotating axis of a hub in which the blade according to the invention is intended to be mounted by the blade root, corresponding to the direction of the centrifugal efforts. It is therefore described as "radially inner" or "proximal" an element located on the hub side in a radial direction of the hub, and "radially outer" or "distal" an element located on the opposite side to the hub in a radial direction of the hub . In a blade according to the invention, the base extends radially inward (proximal) with respect to a passage restriction of the blade root, while the aerodynamic portion extends through the passage restriction. and radially outside said passage restriction. In certain advantageous embodiments and according to the invention, the blade root is also arranged to house the base. Thus, advantageously and according to the invention, the blade root has the opposite of the aerodynamic portion with respect to said restriction of passage (that is to say on the proximal side) and in said direction of retention, a dimension, said proximal width, greater than said restricted width, and the base has a bulk overall in said direction of retention which is less than said proximal width. More particularly, advantageously and according to the invention, the blade root comprises a receiving housing of the base delimited on the side of the aerodynamic portion by at least one restriction of passage in at least one direction of retention, said receiving housing having in said retention direction, a dimension, referred to as the width of the housing, greater than said restricted width, and the base has a bulk overall in said direction of retention which is smaller than said width of the housing so as to be accommodated in this reception accommodation. A passage restriction of a blade according to the invention may be provided solely in a single direction of retention or mainly in a single direction of retention. On the contrary, a passage restriction of a blade according to the invention may be arranged along an angular sector around the radial direction, or even on a complete periphery of the blade root. It forms a neck capable of retaining the aerodynamic portion avoiding its centrifugal ejection in case of breakage of the blade foot assembly. Furthermore, advantageously, a blade according to the invention is characterized in that: - the blade root has a mounting opening having a dimension, called opening width, in any direction, said tangential direction, orthogonal to the direction radial, which is greater than the overall bulk of the base, so that the base can be mounted in the blade root by passage in the radial direction through the mounting opening, - at least one passage restriction according to a retention direction is a restriction of the opening width in said retention direction. It should be noted that the radial direction passes through the mounting opening. The opening width is greater than the overall footprint of the base in said tangential direction so as to allow the passage of the base through this opening during assembly of the aerodynamic portion, the base then being housed in the space -In particular in the receiving housing formed by the blade root- located radially inside said passage restriction. Other embodiments are nevertheless possible in which the mounting of the aerodynamic portion in the blade root is not done by passing through a mounting opening, for example in the case where the blade root is formed of two parts assembled to each other around the base according to a joint plane containing the radial direction. The aerodynamic portion has an aerodynamic surface capable of exerting forces on air. The blade root is advantageously adapted to ensure radial anchoring of the blade in a hub, in particular in a radial shaft of a propeller hub. However, the anchoring of the blade root in a hub is advantageously only radial to allow rotation of the blade about its longitudinal axis (about a radial axis of the hub) to allow the adjustment of the pitch of the blade on the ground and in flight, in particular the automatic adjustment by an adjusting device mounted in the hub of the propeller and connected to the blade root. Advantageously and according to the invention the base has at least one safety bulge defining the overall size of the base 30 in at least one direction of retention. At least one security bulge of the base therefore extends at least in a direction in which the blade root has a passage restriction. The base with such a safety bulge is an integral part of the aerodynamic portion and is therefore free of movable member. Such a security bulge is structurally formed by a portion of the base, wider than the passage restriction, depending on the retention direction at least. Thus, a blade according to the invention does not include any movable or removable element in the aerodynamic portion, so that the blade is both simple to manufacture and maintain, and also less sensitive to vibrations. Advantageously and according to the invention, the dimensions of such a safety bulge are larger in all the directions orthogonal to the radial direction, than the minimum dimension (restricted width) of the restriction of passage in at least one direction orthogonal to the radial direction. The safety bulge and the passage restriction are adapted to be able to radially retain the aerodynamic portion in the blade root against centrifugal forces. In particular, the safety bulge and the passage restriction are sized to be able to withstand the inertia of the aerodynamic portion in rotation, for the maximum acceleration and rotational speed, taking into account the conditions of use, especially on a propeller. turbomachine. The safety bulge and the passage restriction are dimensioned in particular as a function of the material of the aerodynamic portion and of its mass, so as to ensure radial anchoring of the aerodynamic portion relative to the blade root in flight conditions in case of rupture of the assembly at the foot of blade. In particular, the difference between a dimension of the bulge in the direction of retention and a dimension of the restriction of passage, called restricted width, is between 0.5mm and 10cm. This is adjusted according to various criteria including the dimensions of the blade, in particular its size and thickness, its mass, its material, the shape and material of the stops, etc. The safety bulge and the passage restriction are therefore able to provide anchorage of the aerodynamic portion with respect to the blade root in the event of partial or complete breakage of the blade root assembly.
    [0006] Normal operating conditions of the blade are understood to mean conditions in which the blade foot assembly is integral and ensures anchoring of the aerodynamic portion in the blade root at least in said radial direction and advantageously by a locking according to all translation 5 directions and axes of rotation necessary for the proper operation of the propeller. In addition, advantageously and according to the invention, the blade root comprises, in the mounting opening: a first bumper, said intrados bumper, disposed on the side of a lower surface of the aerodynamic portion, a second bumper, said extrados bumper, disposed on the side of an extrados of the aerodynamic portion, the intrados bumper and the extrados bumper forming (between them) said passage restriction. Advantageously and according to the invention, the bumpers are parts attached to the blade root and fixed rigidly to the blade root. The stops are advantageously removably assembled at the blade root. In addition, the mounting opening, in the absence of reported stops forming the passage restriction, is of suitable dimensions to allow insertion of the base of the aerodynamic portion into the blade root through the mounting opening. . Thus, the base of the aerodynamic portion can be introduced simply by the mounting opening before attaching the stops. The assembly of the blade is simple. Advantageously and according to the invention, at least one of the intrados and extrados bumpers can be dismantled by the outside of the blade root. In this way, disassembly of the blade is also possible simply. For example at least one of the stops is fixed to the blade root by screws whose heads are abutted on an outer face of the blade root. Many other means of attachment can be envisaged. Advantageously, a blade according to the invention further comprises at least one member, said buffer, between the aerodynamic portion and the intrados bumper, and at least one member, said buffer, between the aerodynamic portion and the extrados bumper, each buffer being adapted to locally provide a locking of the aerodynamic portion at least in said retention direction. In addition, advantageously and according to the invention, each buffer is mounted with a compressive stress between the aerodynamic portion and one of said stops, said compressive stress being adapted so that any resonant frequency of the blade is distinct from mechanical excitations in conditions of use of the blade. In particular, the material and the compression stress are chosen so that each resonant frequency of the blade is removed from the values of the frequencies of the mechanical excitations in operating conditions of the blade, that is to say for example in flight in the case of an aircraft blade. Said buffers make it possible to ensure an intimate contact between each stopper and a surface of the aerodynamic portion opposite said stopper. Indeed, said buffers are chosen from a sufficiently locally deformable material to be able to compensate for any surface defects of the aerodynamic portion, in particular to compensate for manufacturing tolerances in flatness. This makes it possible to distribute said compressive stress on a surface portion of the aerodynamic portion in a homogeneous manner over this surface portion. In addition, the buffers are chosen from a material adapted to have a stiffness in compression much greater than a stiffness in shear. Thus, they ensure a maintenance of the aerodynamic portion relative to the blade root, but do not prevent the movement of the blade in the radial direction, for example under the effect of a displacement and / or deformation according to this direction 25 when it undergoes centrifugal forces in operation, or in case of breakage of the assembly at the blade root. The buffers are advantageously made of a viscoelastic material. Thus, the absorbent material may be chosen for example from elastomeric materials. The material of each pad being viscoelastic, the buffers are therefore adapted to be able to absorb vibrations between the aerodynamic portion and each stopper (respectively intrados and extrados). The buffer (in particular its material and its dimensions) and the compressive stress are in particular adapted so that any resonance frequency is remote from the vibration frequencies of the blade in operation.
    [0007] The material of the buffers is in particular a stiffness material in compression less than the stiffness in compression of the aerodynamic portion - in particular of a skin forming the intrados and extrados of the aerodynamic portion - and lower than the stiffness in compression of the bumpers.
    [0008] Said buffers can be mounted between the bumpers and the aerodynamic portion in different modes: by gluing on a bumper or on the aerodynamic part, by simple laying - then being held by the compressive stress and the friction on the aerodynamic portion and the bumper - by assembling conjugate shapes of buffer and bumper, etc.
    [0009] The mounting of each buffer between a buffer and the aerodynamic portion is adapted to allow disassembly of the aerodynamic portion relative to the stops, in particular disassembly without particular operation of separation of the buffer of the aerodynamic portion or the stopper. In addition, a blade according to the invention advantageously further comprises, between the aerodynamic portion and each stopper, a deformable member adapted to be able to absorb at least partially the energy of a shock undergone by said aerodynamic portion. This absorbent member is adapted to absorb shocks of large amplitude, for example shocks of the aerodynamic portion with foreign objects such as birds for example. This member is for example formed of a layer of plastically deformable material. This layer of plastically deformable material is for example disposed between each buffer and each stopper, or between the aerodynamic portion and each pad, or between two portions of each stopper, or between the stopper and an anchor fur.
    [0010] However, advantageously and according to the invention, the buffer is chosen from a viscoelastic material adapted to ensure, in addition to the already described functions of the buffer, the function of such an absorbent organ. Advantageously and according to the invention, the intrados bumper and the extrados bumper form a passage restriction of decreasing section in the radial direction towards a free end of the blade. In addition, the base of the aerodynamic portion, and more particularly the safety bulge, has a shape complementary to the passage restriction. Advantageously, this shape is parallelepipedal trapezoidal profile by a section along a plane, said longitudinal plane, containing the radial direction and the direction of retention, so that the forces exerted by the aerodynamic portion in the radial direction are transmitted by the stops to an anchoring fur of the blade root in the direction of retention orthogonal to the radial direction. Furthermore, advantageously and according to the invention, the blade has a strictly positive (non-zero) play in the radial direction between the safety bulge and the passage restriction. Thus, under normal operating conditions of the blade, only the blade foot assembly provides radial anchoring of the aerodynamic portion in the blade root. Advantageously and according to the invention, the blade root comprises an anchoring fur adapted to be mounted in a propeller hub. The blade root comprises an anchoring fur ensuring assembly of the blade root to the hub in cooperation with a hub shaft and the blade foot assembly in cooperation with the aerodynamic portion. The anchoring fur has anchoring means to the hub. The anchoring fur has means for fixing the aerodynamic portion at the blade root adapted to form said blade foot assembly. The blade foot assembly, that is to say the assembly of the aerodynamic portion at the blade root can be the subject of numerous alternative embodiments, and can be carried out in particular by clamping and / or assembly. of shapes and / or by assembly by inserts (bolts, screws, etc.) and / or by bonding and / or brazing and / or by welding and / or by heat treatment allowing a fusion of their respective materials at the interfaces, etc. Advantageously, the blade foot assembly prohibits any relative movement of the blade root and the aerodynamic portion so that it ensures complete attachment of the blade root and the aerodynamic portion. Thus, the blade root provides both a radial locking of the aerodynamic portion relative to a hub including to retain it when it is rotating, and a locking in rotation about the longitudinal axis of the blade (radial relative to the hub) to transmit and maintain pitch adjustment of the blade. Advantageously, a blade according to the invention is also characterized in that: the base of the aerodynamic portion comprises at least one root loop, the blade foot assembly comprises at least one root pin for each root loop: - passing through said root loop, - fixedly assembled at the foot of the blade. In addition, the passage restriction is advantageously offset along the radial direction with respect to the blade root assembly. In some embodiments of the invention indeed, the blade foot assembly is a pivot link. This is particularly the case when the assembly comprises a root pin passing through a single root loop orthogonal axis to the radial direction, so that the aerodynamic portion is locked in translation in the radial direction, and in rotation around the radial direction, but so that it is free to rotate about the axis of the pivot connection thus formed. Thus, the passage restriction being shifted along the radial direction relative to the blade root assembly, the buffers and their buffers block the aerodynamic portion in rotation about the axis of the pivot connection, and take up the moments of bending and the sharp forces of the aerodynamic portion. This arrangement is particularly advantageous insofar as the axis of the root pin is advantageously orthogonal to the thickness (parallel to the chord) of the aerodynamic portion, so that the aerodynamic portion undergoes a high torque around this axis. , the aerodynamic forces exerted mainly on the intrados and the extrados. The blade foot assembly according to the invention advantageously comprises at least one root pin for each root loop. More particularly, it advantageously comprises a single root pin passing through each root loop. Each root pin is anchored - for example by its ends - in the blade root, particularly advantageously in the anchoring fur. For example, a root pin may be a through bolt through the anchoring fur, clamped on each side of the anchor fur. Advantageously and according to the invention, the blade - and more particularly the aerodynamic portion - comprises a single root loop traversed by a single root pin. The assembly and disassembly, therefore the manufacture of a blade and the maintenance of a blade, a propeller, a turbomachine and an aircraft according to the invention are therefore simple. The root loop is advantageously formed at the proximal longitudinal end of the aerodynamic portion in the base. Advantageously and according to the invention, at least one root loop forms a safety bulge. The root loop is advantageously arranged radially inward with respect to the passage restriction. Thus, the blade root assembly is disposed radially inward with respect to the passage restriction. The root loop arranged to allow the passage of a root pin through the base of the aerodynamic portion defines an area of the base of the aerodynamic portion which has the greatest width transverse to the root pin. The root loop thus provides a dual function of anchoring the aerodynamic portion in the blade root in normal operation and safety bulge in degraded operation, that is to say in case of rupture of the assembly of foot of blade.
    [0011] In other words, the root loop has a bulk overall in at least one direction of retention which is greater than the restricted width of at least one passage restriction in this direction of retention. In certain advantageous embodiments, according to the invention, at least one root pin has a space in at least one direction of retention (that is to say a width) which is greater than the restricted width of at least least a restriction of passage in this direction of retention. Indeed, a root pin is formed of a rigid and resistant material, so that in case of breakage of the blade root assembly, the root pin abuts against the restriction of passage (with a thickness of the root loop interposed between the pin and the restriction of passage) retains the aerodynamic portion with efficiency and safety. Breakage of the blade root assembly may be due in particular to breakage of the anchor fur at anchor points of the root pin and / or breakage of the root pin, and or rupture of the root loop. In addition, advantageously, a blade according to the invention comprises at least one insert disposed in at least one root loop, said insert having a socket for receiving a root pin forming an axis of the foot assembly. of pale. The insert is inserted into the root loop and has outer dimensions corresponding to the inner dimensions of the root loop, which it can impose at least in part. Advantageously and according to the invention, the insert is assembled to the root loop, for example by bonding and / or heat-bonding and / or copolymerization and / or welding and / or assembly and / or soldering, etc. Advantageously and according to the invention, the insert is a rigid part in compression, that is to say non-deformable under the effect of the stresses that it can undergo in operation, in particular because of the forces applied by the control loop. root on this insert. The insert thus ensures a maintenance in the shape of the base - in particular of the root loop - of the aerodynamic portion. The internal dimensions of the sleeve of the insert 5 advantageously correspond to the outer dimensions of the root pin which is housed in this socket. The insert advantageously provides the mechanical connection between the root loop and the root pin. In particular, it provides anchoring in the radial direction at least of the aerodynamic portion relative to the root pin. Advantageously and according to the invention when the base of the aerodynamic portion comprises several root loops, each root loop comprises an insert. A blade according to the invention is furthermore advantageously characterized in that the aerodynamic portion is at least partly made of composite material comprising at least a majority of unidirectional fibers in the radial direction and wound in the base of the aerodynamic portion around said insert to form at least one root loop. Advantageously and according to the invention, the insert may be formed of a metallic or synthetic material, in particular a composite material. Throughout the text, the term "composite material" refers to any heterogeneous synthetic solid material associating at least two phases. This term particularly denotes a material comprising at least one fibrous reinforcement and at least one matrix, the fibrous reinforcement, formed of a first material, being adapted to give mainly strength properties (at least in tension and / or in flexion). and / or in shear) to said composite material, and the matrix, formed of at least a second polymeric material, providing shaping, protecting the reinforcement and transmitting certain stresses to it, and being able to participate in compressive strength and / or or in torsion. Having the unidirectional fibers forming the fibrous reinforcement of a composite material constituting at least part of the aerodynamic portion in the direction of the span makes it possible to optimize the resistance of the aerodynamic portion to the forces causing bending of the blade . In addition, these unidirectional fibers arranged in a winding around the root pin according to the shape of the root loop confer a very high resistance to the assembly of blade root. Advantageously and according to the invention, said unidirectional fibers are chosen from the group consisting of carbon fibers, aramid fibers, carbon-aramid fibers, glass fibers, natural fibers such as hemp or bamboo fibers, metal fibers, and mixtures thereof. Other fibers may be used in accordance with the invention. Any length of fibers may be considered, if necessary in mixtures. Advantageously and according to the invention, the aerodynamic portion comprises a chord and a hollow envelope, said chord being disposed in the hollow envelope. The hollow envelope ensures the aerodynamic function of the blade. In particular, the hollow envelope forms the intrados and extrados and allows a flow of fluid, especially air, around the blade. The chord ensures the maintenance of the shape of the hollow envelope and its anchoring in the blade root. The frame comprises for example longitudinal members and / or ribs. The hollow envelope and the chord are advantageously made of composite material. Advantageously and according to the invention, each of the parts of the blade is formed of a composite material. Nothing prevents, however, to optionally provide that at least a blade portion, for example the blade root, is formed of a non-composite material, for example a metal alloy.
    [0012] In addition, advantageously and according to the invention, the different parts of the blade formed of composite material (x) have a polymer matrix consisting mainly of at least one compound belonging to the same chemical family, which is therefore common to the polymer matrix of the composite material (s) constituting these different parts. Advantageously and according to the invention, the different parts of the blade formed of composite material (x) comprise the same polymer matrix.
    [0013] Advantageously and according to the invention, each polymer matrix is chosen from the group consisting of epoxy resins, polyurethane resins, phenolic resins, polyester resins, cyanate esters, vinylester resins, bismaleimide resins (BMI), thermoplastics, and their mixtures. Other examples are possible. The invention also extends to a turbomachine propeller comprising at least one blade according to the invention. A blade according to the invention can in particular advantageously be used on an aircraft turbomachine propeller, in multiple copies. Thus a turbomachine propeller according to the invention advantageously comprises at least two blades, particularly advantageously between three and eight blades according to the invention. A propeller according to the invention also advantageously comprises a central hub driven by a motor, and in general a device for continuously monitoring the pitch of the blades. The central hub has a plurality of radial barrels distributed radially around the hub and in each of which a blade root comprising an anchor fur is mounted. In particular, a propeller according to the invention comprising a plurality of blades according to the invention may advantageously be mounted on any type of turbomachine.
    [0014] A propeller according to the invention takes advantage of the advantages of the blades according to the invention and is particularly particularly safe and easy to maintain, also allowing easy replacement of each blade. The invention also extends to a turbomachine comprising at least one propeller according to the invention. A turbomachine according to the invention advantageously comprises one or more propellers according to the invention. When the turbomachine comprises a plurality of propellers according to the invention, the latter can for example be counter-rotating. The invention also extends to an aircraft comprising at least one turbomachine according to the invention. An aircraft comprising one or more propeller turbomachines comprising blades according to the invention is particularly advantageous. Such an aircraft is particularly safe thanks to the safety bulge and the passage restriction, capable of preventing the ejection of a blade in the event of breakage of its blade foot assembly. The aircraft advantageously comprises one or more turbomachines according to the invention.
    [0015] The maintenance of such an aircraft is also facilitated by one or more blades according to the invention. The invention also relates to a propeller blade, a turbomachine propeller, a turbomachine and an aircraft characterized in combination by all or some of the characteristics mentioned above or below.
    [0016] Other objects, features and advantages of the invention will become apparent on reading the following non-limiting description which refers to the appended figures in which: FIG. 1 is a diagrammatic perspective view of the foot and An aerodynamic portion of a blade according to an embodiment according to the invention, - Figure 2 is a schematic sectional view through a radial plane orthogonal to the axis of the root pin of the blade of the figure 1, - Figure 3 is a schematic sectional view through a radial plane comprising the axis of the root pin of the blade of Figure 1. 20 An aircraft turbine engine propeller blade according to the invention presented in the figures comprises a blade root 20 and an aerodynamic portion 21, a part of which, said base, extends in the blade root, the aerodynamic portion 21 passing through an opening, said mounting opening 27, the blade root. The blade root 20 comprises a hollow anchor 22 of generally cylindrical shape around a radial direction 23 corresponding to a direction of the centrifugal forces applied to the blade when it is rotated with the anchored blade root. to a rotating hub. The radial direction therefore corresponds substantially to the span of the blade. The anchoring fur 22 has, in the radial direction 23, a proximal end 30 closed by a lid 29 and an open distal end forming said mounting opening 27.
    [0017] The blade root 20 further comprises an intrados bumper 24 and an extrados bumper 25 removably mounted on the anchoring fur, for example by screws 28, in the mounting opening 27, so as to restrict its width. and to form a passage restriction 30 along a direction, referred to as the retention direction 38, orthogonal to the radial direction 23. Throughout the rest of the text, the term width and its derivatives refer, unless otherwise indicated, to a dimension in the direction of Retention 38. The passage restriction 30 thus has a restricted width relative to the width of the mounting opening 27 in the retention direction 38.
    [0018] The anchoring fur 22 forms a housing 40 for receiving the base of the aerodynamic portion 21, the internal dimensions of this receiving housing 40 being adapted to allow housing of this base in the housing 40. In particular, the width of the housing 40 reception is greater than or equal to the overall width of the width of the base of the aerodynamic portion 21. The receiving housing 40 is delimited radially outwardly by the passage restriction 30. The mounting opening 27 presents also preferably internal dimensions adapted to allow the passage of the base through the mounting opening 27 when it is placed in the housing 40 of reception. In particular, the mounting opening 27 has a width in the retention direction 38 which is greater than the overall width of the width of the base of the aerodynamic portion 21. The base of the aerodynamic portion 21 therefore extends radially. on the inside with respect to the passage restriction 30, and has a safety bulge 31 of outer dimension 32 (bulk overall width) in said retention direction 38 strictly greater than the restricted width of the passage restriction 30 according to said direction of retention. For example, the outer width 32 of the safety bulge 31 is 32 mm and the restricted width of the passage restriction 30 is 22 mm.
    [0019] The safety bulge 31 of the base of the aerodynamic portion is formed by a root loop 37 of the base of the aerodynamic portion. In particular, the root loop 37 is formed of the proximal end of a spar forming part of the chord of the aerodynamic portion. The root loop 37 receives an insert 33 having an axially through bushing 34 in which a root pin 35 is mounted. The root pin 35 is a rigid straight shaft extending in a longitudinal direction defining an axis 36 of the blade foot assembly. The root pin 35 is mounted at both ends in root housings formed in the anchoring fur 22, preferably between the proximal end of the anchor fur 22 and the lid 29 attached thereto. by screws 42. The longitudinal direction of the root pin 35 is orthogonal to the radial direction 23, and orthogonal to the retention direction 38. The same is true of the axis 36 of the blade foot assembly defined by the root pin 35. The root loop 37, the insert 33, the root pin 35 and the root housings form the blade root assembly, i.e. assembly of the aerodynamic portion in the blade root. The overall width of the base of the aerodynamic portion 21 is defined by the root pin 35, the thickness of the root loop 37 and the insert 33. Preferably, this overall bulk width is imposed by the root pin 35 and the insert 33 which are rigid parts in compression. Preferably, the width of the root pin 35 and / or the maximum width of the insert 33 is strictly greater than said restricted width of the passage restriction 30. Each stopper 24, 25 is equipped with a member, said buffer 26, disposed between the aerodynamic portion 21 and said stopper 24, 25. The pads 26 are preferably formed of pads attached to the end of each stopper and made of a viscoelastic material, for example elastomeric material.
    [0020] The bumpers 24, 25 and the pads 26 block the aerodynamic portion 21 in rotation about the axis 36 defined by the root pin 35. They allow to take up the bending moments and the shearing forces of the aerodynamic portion 21.
    [0021] The bumpers 24, 25 have abutment surfaces inclined relative to the radial direction 23. The pads 26 have surfaces in contact with the aerodynamic portion which are also inclined relative to the radial direction 23. The inclination of each bumper corresponds advantageously at an inclination of the portion of the base of the aerodynamic portion 21 which comes into contact with said intrados bumper 24 and with said bumper extrados 25 in case of breakage of the blade root assembly. The inclination of the stops 24, 25 is chosen to take up the forces exerted by the aerodynamic portion on the blade root in the event of breakage of the blade root assembly, in the radial direction 23. The inclination of the stops 24, 25 is for example advantageously between 50 and 45 °, in particular advantageously of the order of 10 degrees. In addition, the pads 26 and / or their assembly to the stops 24, 25 are adapted so that in case of breakage of the blade foot assembly, the pads 26 provide no radial retention 23 of the aerodynamic portion. The pads 26 may for example be glued to the stops or simply interposed between the bumpers and the aerodynamic portion or assembled to the bumpers by conjugate forms of the buffers and bumpers. In other words, the buffers 26 do not participate in the restriction of passage, the restricted width of the restriction of passage being defined between the internal faces facing the two stops 24, 25, without taking into account the pads 26. Thus, there is a a strictly positive clearance, defined by the thickness of the pads 26, between the restriction of passage 30 and the safety bulge 31 in the radial direction 23 so that in case of breakage of the blade root assembly, the aerodynamic portion 21 is displaced in the radial direction 23 until it abuts against the intrados bumper 24 and against the extrados bumper 25, ejecting the buffers 26.
    [0022] Furthermore, the anchor fur 22 advantageously has paths 41 of balls to be mounted in a hub for anchoring the blade (in particular the blade root) in the hub in said radial direction 23 and while allowing adjustment of the not of the blade by a rotation thereof around the radial direction 23. Other rolling elements can be envisaged. The spar of the aerodynamic portion forming the root loop 37 is made of a composite material, preferably comprising a reinforcement of carbon fibers arranged longitudinally along the span (in the radial direction 23) of the blade in an epoxy resin matrix, said carbon fibers being wound in the base to form the root loop 37. The assembly of a blade according to the invention is carried out as follows. The aerodynamic portion 21 is introduced into the anchoring fur 22 15 by passing the base through the mounting opening 27. The two stops 24, 25 equipped with their pads 26 of elastomer are fixed in the opening 27 of mounting by the screws 28 so as to form the passage restriction. The root pin 35 is inserted into the bushing 34 of the insert 33 and into the root housing portions formed by the anchoring fur 22. The cover 29 is then screwed onto the anchor fur 22 to rigidly locking the root pin 35, preferably by applying a clamping stress of the root pin 35. The dimensions of the different parts are preferably adjusted so that the buffers 26 of the stops 24, 25 are slightly prestressed in compression. The insert 33 is also advantageously made of a molded composite material comprising a reinforcement of carbon fibers in an epoxy resin matrix. The intrados bolsters 24 and extrados 25 are preferably metal, for example titanium alloy. The anchoring fur is preferably metal, for example steel alloy.
    [0023] A blade according to the invention is particularly simple, has a single axis and a single receiving sleeve of this axis (sleeve 34) for precise adjustment and easy assembly, minimizing the problems of adjustment between the different parts. It is particularly light, most of these component parts, limited in number, can be made of composite material. The damping pads 26 are removable and easily replaceable. The aerodynamic portion 21 is independent of the blade foot assembly from the point of view of these components and the transmission of forces, and may be any, the invention being applicable to all kinds and shapes of blades.
    [0024] The blade foot assembly makes it possible to apply a slight preload to the axis 36. The geometry of the various parts is particularly simple and facilitates their manufacture, in particular with regard to the anchoring fur 22 and the insert 33. The number of pieces bonded to each other is minimum, the transfer of efforts being mainly by compression. A loss of blade is possible only with a break of at least twice the blade foot assembly, so that a blade according to the invention resists a single break. The invention can be the subject of many other embodiments not shown. In particular, nothing prevents the blade foot assembly from being disposed radially outside the intrados and extrados 25 stops, provided that the aerodynamic portion always has a bulge radially inside said stops. The anchoring fur can be monobloc.
    权利要求:
    Claims (2)
    [0001]
    CLAIMS1 / - blade comprising: - a blade root (20), - an aerodynamic portion (21), a part of which, said base extends into the blade root, - an assembly, said blade foot assembly, of the aerodynamic portion at the blade root retaining the aerodynamic portion in a direction, said radial direction (23), corresponding to a centrifugal direction when the blade is rotated with the blade root anchored to a rotating hub, characterized in that : the blade root comprises at least one restriction of passage in at least one direction, said direction of retention, orthogonal to the radial direction, said passage restriction having, in said direction of retention, a dimension, called restricted width, allowing the passage of the aerodynamic portion (21) through the restriction of passage, - the base extends radially inward with respect to said restriction of passage, and has a bulk overall in said direction of retention strictly greater than said restricted width, so that in case of breakage of the blade root assembly, the base is capable of abutting in said radial direction against the restriction of passage of the blade. in order to retain the aerodynamic portion (21) in the blade root (20) at least in said radial direction (23).
    [0002]
    2 / - blade according to claim 1, characterized in that: - the blade root has a mounting opening (27) having a dimension, said opening width, in any direction, said tangential direction, orthogonal to the direction radial, which is greater than the overall footprint of the base, so that the base can be mounted in the blade root by passage in the radial direction through the mounting opening (27), - at least one restriction in a direction of retention is a restriction of the opening width in said retention direction. 3 / - Blade according to claim 2, characterized in that the blade root (20) comprises, in the opening of assembly (27): - a first bumper, said intrados bumper (24), disposed on the side of a lower surface of the aerodynamic portion, - a second bumper, said bumper extrados (25), disposed on the side of an extrados of the aerodynamic portion, the intrados bumper (24) and the goal extrados (25) forming said passage restriction (30). 4 / - blade according to claim 3, characterized in that it further comprises at least one member, said buffer (26) between the aerodynamic portion (21) and the intrados bumper (24), and at least one member, said buffer (26), between the aerodynamic portion (21) and the extrados bumper (25), each pad (26) being adapted to locally provide a locking of the aerodynamic portion in at least one direction orthogonal to the radial direction (23) . 5 / - blade according to claim 4, characterized in that each pad (26) is mounted with a compressive stress between the aerodynamic portion (21) and one of said stops (24, 25), said compressive stress being adapted so that any resonant frequency of the blade is distinct from mechanical excitation frequencies under conditions of use of the blade. 6 / - blade according to one of claims 3 to 5, characterized in that the intrados bumper (24) and the extrados bumper (25) form a restriction of passage section (30) decreasing in the radial direction towards the a free end of the blade. 7 / - blade according to one of claims 1 to 6, characterized in that it further comprises, between the aerodynamic portion (21) and each stopper (24, 25) a deformable member adapted to be able to absorb at least partially the energy of a shock experienced by said aerodynamic portion (21). 8 / - Blade according to one of claims 1 to 7, characterized in that the base has at least one bulge (31) security defining the overall size of the base in at least one direction of retention. - blade according to one of claims 1 to 8, characterized in that the blade root comprises an anchor fur (22) adapted to be mounted in a propeller hub. 10 / - blade according to one of claims 1 to 9, characterized in that: - the base of the aerodynamic portion (21) comprises at least one root loop (37), - the blade foot assembly comprises at least one root pin (35) for each root loop: - passing through said root loop, - fixedly joined to the blade root. 11 / - blade according to claims 8 and 10, characterized in that at least one root loop (37) forms a safety bulge (31). 12 / - blade according to one of claims 10 or 11, characterized in that it comprises at least one insert (33) disposed in at least one root loop (37), said insert having a socket (34) receiving at least one root pin (35). 13 / - blade according to claim 12, characterized in that the aerodynamic portion (21) is at least partly composite material 20 comprising at least a majority of unidirectional fibers in the radial direction (23) and winding in the base the aerodynamic portion around said insert (33) to form at least one root loop (37). 14 / - Turbomachine propeller comprising at least one blade according to one of claims 1 to 13. 25 / - Turbomachine comprising at least one propeller according to claim 14. 16 / - Aircraft comprising at least one turbomachine according to claim 15. 30
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3021030A1|2015-11-20|SECURED ANCHOR BLADE IN RADIAL TRANSLATION, PROPELLER, TURBOMACHINE AND AIRCRAFT
    EP0121462B1|1987-11-04|Multi-blade variable pitch propeller with individually detachable composite material blades
    EP0080920B1|1985-07-31|Rotor for rotor craft with articulated joints incorporated in the blade root
    CA2055953C|1997-04-22|Rotary wing aircraft rotor hub beam
    EP0604299B1|1997-01-29|Blade-hub lamellar connection device, rotor blade and rotor featuring it
    FR2984847A1|2013-06-28|REDUNDANT ANCHOR BLADE IN A HUB, PROPELLER, TURBOPROPULSEUR AND AIRCRAFT
    EP2723642A1|2014-04-30|Structure for mounting a turbine engine
    EP0213016A1|1987-03-04|Mast hub unit and rotor head for a rotor craft incorporating it
    FR2925015A1|2009-06-19|ROTOR BLADE OF GIRAVION, ROTOR OF GIRAVION PROVIDED WITH SAID BLADE, AND METHOD OF MANUFACTURING THE BLADE
    EP0549454B1|1996-05-22|Articulated rotor head for a rotorcraft
    EP0521792B1|1995-09-06|Rotary wing aircraft rotor head, rigid in drag and articulated in pitch and flapping
    FR2984848A1|2013-06-28|PROPELLER BLADE WITH HOUSINGS AND REINFORCING LENGTHS AND PROPELLER COMPRISING AT LEAST ONE SUCH BLADE
    FR2778165A1|1999-11-05|Helicopter rotor with pre-stressed blade root over sleeves support half-bearings
    EP2803571A1|2014-11-19|Resilient hinged connection between a lag-lead damper and a rotor blade
    FR2569243A1|1986-02-21|Variable-pitch propeller rotor, in particular for a wind machine
    WO2012049399A1|2012-04-19|Assembly for attaching the hangers from which an aircraft propulsion unit is suspended
    WO1998056656A1|1998-12-17|Gyroplane rotor with double-plate hub and external pitch control
    EP3309069B1|2019-04-17|A lead-lag damper integrated inside a blade of a rotor
    WO2022018358A1|2022-01-27|System for controlling the pitch setting of a propeller blade for an aircraft turbine engine
    WO2022018357A1|2022-01-27|Aircraft turbine engine comprising variable-pitch propeller blades
    WO2022018354A1|2022-01-27|System for controlling the pitch of a propeller blade for an aircraft turbine engine
    WO2022018356A1|2022-01-27|Assembly comprising a blade and a blade pitch setting system
    FR3112820A1|2022-01-28|AIRCRAFT TURBOMACHINE WITH VARIABLE-PITCHED PROPELLER BLADE
    FR3112819A1|2022-01-28|AIRCRAFT TURBOMACHINE COMPRISING VARIABLE-PITCHED PROPELLER BLADE
    EP0493195B1|1995-06-28|Rotorcraft articulated rotor head with intermediate blade root cuff
    同族专利:
    公开号 | 公开日
    US9840921B2|2017-12-12|
    FR3021030B1|2018-01-05|
    US20150330233A1|2015-11-19|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3734642A|1971-06-29|1973-05-22|United Aircraft Corp|Aerodynamic blade root end attachment|
    FR2984847A1|2011-12-23|2013-06-28|Ratier Figeac Soc|REDUNDANT ANCHOR BLADE IN A HUB, PROPELLER, TURBOPROPULSEUR AND AIRCRAFT|
    EP2677121A2|2012-06-22|2013-12-25|Rolls-Royce plc|A catcher ring arrangement|EP3756994A1|2019-06-27|2020-12-30|Airbus Helicopters|Displacement propeller provided with interchangeable blades and method for mounting interchangeable blades on a displacement propeller|
    WO2022018356A1|2020-07-24|2022-01-27|Safran Aircraft Engines|Assembly comprising a blade and a blade pitch setting system|US1769801A|1924-11-15|1930-07-01|Hamilton Standard Propeller Co|Propeller|
    FR2542695B1|1983-03-18|1985-07-26|Aerospatiale|MULTI-BLADE PROPELLER WITH VARIABLE PITCH WITH BLADES IN COMPOSITE MATERIALS INDIVIDUALLY REMOVABLE, PROCESS FOR MANUFACTURING SUCH BLADES AND BLADES THUS REALIZED|
    US5102300A|1988-10-07|1992-04-07|United Technologies Corporation|Pinned airfoil propeller assembly|
    FR2682722B1|1991-10-16|1994-01-21|Jeumont Schneider|MEANS FOR THE ANCHORAGE OF A PART IN RELATION TO ANOTHER.|
    US6102664A|1995-12-14|2000-08-15|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Blading system and method for controlling structural vibrations|
    FR2970943B1|2011-01-31|2014-02-28|Eurocopter France|BLADE AND METHOD FOR MANUFACTURING THE SAME|
    FR2984848B1|2011-12-23|2016-01-15|Ratier Figeac Soc|PROPELLER BLADE WITH HOUSINGS AND REINFORCING LENGTHS AND PROPELLER COMPRISING AT LEAST ONE SUCH BLADE|
    US9505489B2|2013-03-13|2016-11-29|Bell Helicopter Textron Inc.|Flexing clevis arrangement bolted joint attachment for flexible rotor hub with high offset and high flapping|FR3050719B1|2016-04-28|2018-04-13|Airbus Operations|AIRCRAFT TURBOMACHINE PROPELLER COMPRISING MEANS OF FLAME-RELIEVING BACK-UP MEANS|
    FR3050718B1|2016-04-28|2022-02-18|Airbus Operations Sas|PROPELLER FOR AIRCRAFT TURBOMACHINE COMPRISING SIMPLIFIED PROPELLER BLADE RADIAL RETENTION MEANS|
    FR3085415B1|2018-09-05|2021-04-16|Safran Aircraft Engines|DAWN INCLUDING A COMPOSITE MATERIAL STRUCTURE AND A METAL SHELL|
    US11092020B2|2018-10-18|2021-08-17|Raytheon Technologies Corporation|Rotor assembly for gas turbine engines|
    FR3087830B1|2018-10-30|2020-10-16|Safran Aircraft Engines|DAWN INCLUDING A STRUCTURE IN COMPOSITE MATERIAL AND A METAL STRENGTHENING PART|
    US11059566B2|2019-10-02|2021-07-13|Bell Textron Inc.|Additive manufacture proprotor blade|
    US11073030B1|2020-05-21|2021-07-27|Raytheon Technologies Corporation|Airfoil attachment for gas turbine engines|
    US20210404516A1|2020-06-30|2021-12-30|Bell Textron Inc.|Rotor retention fitting with integral bearing and pitch control|
    WO2022018358A1|2020-07-24|2022-01-27|Safran Aircraft Engines|System for controlling the pitch setting of a propeller blade for an aircraft turbine engine|
    法律状态:
    2015-05-22| PLFP| Fee payment|Year of fee payment: 2 |
    2015-11-20| PLSC| Search report ready|Effective date: 20151120 |
    2016-05-23| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-23| PLFP| Fee payment|Year of fee payment: 4 |
    2018-05-29| PLFP| Fee payment|Year of fee payment: 5 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-06-19| PLFP| Fee payment|Year of fee payment: 8 Year of fee payment: 7 |
    2021-05-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1454283A|FR3021030B1|2014-05-14|2014-05-14|SECURED ANCHOR BLADE IN RADIAL TRANSLATION, PROPELLER, TURBOMACHINE AND AIRCRAFT|
    FR1454283|2014-05-14|FR1454283A| FR3021030B1|2014-05-14|2014-05-14|SECURED ANCHOR BLADE IN RADIAL TRANSLATION, PROPELLER, TURBOMACHINE AND AIRCRAFT|
    US14/712,094| US9840921B2|2014-05-14|2015-05-14|Blade anchored securely in radial translation, propeller, turbine engine and aircraft|
    [返回顶部]